Turbine



March 19, 1935. BROOKE 1,994,501

TURBIINE 3 Sheds-Sheet 1 Filed March 17, 1933 INVENTO Bani-K March 19,1935. F BROOKE 7 1,994,501

TURBINE Filed March 1'7, 1933 5 Sheets-Sheet 2 F. M. BROOKE TURBINEMarch 19, 1935.

Filed March 1'7, 1933 War wn'm ES 5 E5 @1133 BM 3 Sheets-Sheet 3Patented Mar. 19, 1935 PATENTo-FFICE TURBINE n Francis M. Brooke, BrynMawr, Pa... assignorto Nanna S. Brooke, Bryn Mawr, Pa.

Application ;March 17,. 1933, Serial No.f6 61,24s; I 401mm. (or. 2539165This invention relates to elastic bower.

units, andmore particularly to axsteamor turbine of the double-rotortype. l The primary object of my invention. is to gas shorten the lengthof such turbines while' utilizing the normal applied effort,substituting for the stator blades, in an ordinary axialflow. turbine, asecondary or double set of rotor blades.

Another objectis to increase, the'effic iency of 10:; such a turbine byhavingrotor blades. receive effective effort from the gas, wherepreviously the stator blades only straightened the path of the gas,under the theory that every time a particle strikes a surface therefractory force loses a certain amount of energy consumed by impact.

A further object is to permit the useof gas or steam at a highervelocitythan hereto-fore, with the same degree of safety.

A. still further object is to enablelighter. construction of turbines,at a .given steam or gas velocity, without decreasein efficiency. l

The stated objects; with incidental advantages, are attained by theembodiment of; my invention illustrated in the accompanying sheets ofdraw-- ings; while the claims at the conclusion'of the followingdetailed explanation of said drawings, succinctly; define the featuresof novelty-over prior art. I v .Fig. I is a longitudinal section of myimproved turbine. n r Fig. II is a longitudinal sectional continuationat the left-hand endof Fig.1.

Fig. III is anelevation of the turbine at the exhaust end. I

Fig. IV is a fragmentary cross-section of the turbine taken along theline AA' in Fig. 1.. Fig. V is a side elevationofa-sprocket-holdingcage-hereinafter fully described. n Fig. VI is a parallelogramillustrating the travel of arotor blade in relation tothe travel ofthegas in an ordinary turbine.

. Fig. VII is a parallelogram illustrating the double rotor travel inrelation to the travel of the gas in my improved turbine as hereinafterdescribed.

Fig. VIII illustrates the traveler the gas from a rotor to a stator, toa rotor 'blade, injan ordinary turbine. 1

Fig. IX shows the-travel of the gas froma rotor to a rotor revolving inthe opposite direction, which isused in place, of a stator, to a thirdrotor blade; and, I n

Fig- X shows the path of two molecules of gas impinging on severalrotorb'ladesh Inall the. views corresponding reference charactersdesignate the same or similar parts.

Referring. to Fig. I, the rotor shaft 1 is sup ported by endbea n s 2,which ar held in place bvsllpp'ortst that are secured on the base i. 5,

On], this shaft, 1, is fixed the first rotor which is comprehensivelydesignated 5 to which are fixed rotor blades. 7,]and which rotatesclockwise.

A support 9. holds in position an extension 10 of the manifold inletpipe 11., The manifold 11 10 and extension 10, areretained in positionby bolts. 12. and nuts 13 while leakage is prevented by askets. 1d. Itmay belloted that the extension 10. has spaces 15. for circulation ofwater, which is conveyed to and from 10 by pipes 16. Qn the 15 extension101$ Screwed alcollar 17,1which is [adjustable avinga pace. law be.filled with Ra ing and thusserving. as a stuffin box to prevent 1 akasThe. outer surface. of.v the collar 17 is a fine .0 bearing surfaceexcepting at the far end from thestuffing bon where it is threaded aconvenient distancefor fitment or a collar 22. The second rotor, which.is. comprehensively designated as 6, on. wh ch are. fastene ro or blades.8. is. m in two or morelongitudinal sectionanot, specifically md cat d,that are bolted to ethe in a nc wi h know p actice- In. assembling, theturbine, the collar 1'7 is screwed on the extension 10 in approximatelythe position shown. Shaft 1 with rotor 5 is next placed. in. position.Collar, 17. is screwed to approximately the position shown and thepacking firstinserted inspace 18.. The sections of the second rotor ,6,are then. bolted together so that blades 8, 7 are spaced. between, eachother as shown. Balls 19 are then placedin position and col1ar20. is.suitably secured to rotor 6. Collar 22 is then-screweda littledistance.along the collar 17. and balls 21 inserted, whereupon said collarisscrewed sufficiently far along the collar 1'7 to retain the balls 21in the groove preparatory to maladjustment. n large collar 23, afterhaving packing put in the stuffing bl X. space 251 is fixed in theapproximate position as shown. Balls 25 are then placed inthegrooveshown and, the collar 26 secured in place to. retain. saidballs25in position. Later perfect adjustment is obtained by moving thecollars17, 23, so as'to' make the packing in spaces 2&1 and 18 tight,whereupon the collars 22 and 26 are manipulated so as to perfectly spacethe rotor blades '7, 8 of the rotors 5, 6. It may now be noted thatrotor 6' can rotate freely on the rotor 5. at the exhaust end of theturbine and onthe 5 counterclockwise. placed so that when gas .or steampasses through,

extension inlet manifold 10 at the inlet end, furthermore that leakagebetween the two rotors is effectively stopped by the packings at 18 and24.

The privilege is reserved of utilizing other than ball bearings, such assmooth roller bearings, etc., rather than annular ball or thrust ball;or the annular contact ball bearing which is used both as a thrust andan annular bearing herein. Furthermore, in both spaces 18 and 24' otherthan common packing may be used to ensure the most perfect gas fit witha minimum of resistance and more durable nature.

On the rotor 6, at the extreme right end, are gear teeth 27 and on therotor 5 there is a collar 28 having gear teeth 29. In Fig. IV these gearteeth 27, 29 are clearly illustrated. A cage 32, shown more clearly inFig; V, which carries spur gears 38 is placed in position, as shown inFig. I, such spur gears 38 being located in mesh between the large gears29 and 27. Spur gears 38 rotate on stub shafts 30, which are secured inthe'cage 32 and set a distance from said cage by washers or spacers 34.If preferredthe stub shafts or pins 30 can rotate in the cage 32, asthere is more room there for a bearing surface. It is obvious that whenspur gears 38 are meshed with the planetary gears 2'7 and 29 and therotor 5 is ro-' tatedclockwise, that the rotor 6 would be rotated Blades7 on the rotor 5 are the turbine 5 will rotate clockwise; In like mannerthe blades 8 of the rotor 6 are at such an will absorb the power fromthe rotor 5 and have a tendency to slow its rotation, However, the de- 1sign of the turbine being such that, the resistance being equal, bothrotors'5, 6 will revolve at equal speed but in opposite directions, thetendency for. rotor 6 to run at high speed being offset by spur gears 38which transmit equal resistance from rotor 5 to rotor 6, and gears saidrotors so that they must rotate at approximately equal speed, while thedriving force of rotor 6 is trans ferred to that of rotor 5 and'thedirection is reversed by the spur gears 38 so that the effective effortof both said rotors is conveyed to shaft 1 rotating clockwise.

An exhaust manifold 36 is placed over the circular exhaust ring 35 andoverlaps the latter by a peripheral projection 3'7, and to which eitherpiston rings or stuffing boxes may befitted if desir-' able to make thejoint gas-tight toa high degree, though the pressures at this point below.

The manifold 11 is made fast to the extension 10 and a gland 39, whichscrews on the body i1 of the stufring box 40, is put in place withsuitable packing in the space 42. .Other means to ensure a gas-tightjuncture may be utilized at this point, if desired. The turbine is nowliftedin place, the shaft 1 resting in its supporting bearings 2,. onthe sup: ports 3, whereupon the cage 32 is made fast to the base 4 bybolts 31. Exhaust pipe 42, which is a part of the exhaust manifold 36,shown in Fig. III, also embodies supports 43 of the cage 32. The variousadjustments as to bearings and stufi'mg boxes previously referred to cannowv be made.

It is evident that a turbine as above described, with two rotors 5, 6,having alternate rows of blades rotating in opposite directions, willpro 1 vide a rotor blade area against the infiowing gases that is verymuch shorter than a conventional rotor, and accordingly a much shorterturbine than where following each row of rotor blades in the ordinaryturbine there is a row of stator blades of approximately the same width.In other words the rotor blades 7, 8 in each case function not only assuch but also as stator blades.

The second object of increasing the efficiency of the turbine isachieved as the friction losses of the stator blades are removed,"whereintheordinary turbine stator'blades contribute only the straightening ofthe path of the motive fluid to the desired angle, and the effortexerted against line a, b, one-half the length of a, d, represents thevelocity of the average rotor blade; therefore, a, d represents thevelocity of the gas or steam, straight through the turbine.

Fig. v11 shows the line a, b, b" which equals" a, b in Fig. VI,depicting the same relation, though a, b and b, b" that are in oppositedirections are of equallength, the velocity of the first rotor,

described as a, b in Fig. VI, could be equaled by the velocity of eachof the double rotors e xpressed bya', b" and b, b in Fig.VII.

k In Fig. VIII there are the rotor blades 0 and and stator blade I), theline a, b, 0 shows the path of a molecule of gas passing from a rotorblade, to a stator blade, then to a second rotor blade in anordinarysingle rotor turbine.

Fig. IX is similar to Fig. VIII, but in which b is changed to a' rotorblade which rotates'aw'ay from a and c demonstrating a path of equallength, i. e., a, b, c=a', b, c, which is obtainable in both Figs. VIIIand IX, when a! and c in Fig. IX move one-half as fast as a, 0 providedb moves in the opposite direction at aspeed equal to that of a and 0'.

Fig. X shows molecules of gas m and m in a line from a rotor blade, withm impinging on the blade 2. Dotted blade 2' shows its positionwhenreached by m Rotor blade 3, travelling inthe O posite directionshows the subsequent position of m'when they contact, and dotted blade 3its position when reached by m In these flgures it is assumed the gas orsteam until deflected, travels in a straight line and with twice thevelocity of the rotor blades, and the angle of incidents is equal to theangle of refraction, with the correcas v stator blade between that ofone striking a moving rotor blade. The reaction in a line normal to theblade being the difference in velocities of the molecule and blade inthe same direction. Therefore, to equal this eifect at a given gas orsteam speed against a stator, the said speed along the normal line wouldhave to be increased by the rotor speed in the same direction.

Accordingly, higher gas velocities are obtainable when the stator bladesmove away from the gas or steam like rotor blades, or all blades have adual function, serving as both stator and rotor blades. v

Having thus described my invention, what I claim is:

1. In an axial flow turbine the combination of inner and'outerconcentric flaring rotors each embodying circumferential rows ofrespectively alternating reversely-directed blades, said inner rotorbeing rigidly secured on the turbine shaft and embodying an annularexhaust chamber at the larger end for coaction with a stationarilymounted outlet manifold, said outer rotor being antifrictionally mountedfor revolution in a reverse direction about the inner rotor, whereby allof the blades function in the dual capacity of impact and reactionelements, and planetary gearing including toothed rings with anindividual cage-like structure supporting intermeshing spur gears aboutthe annular exhaust end of the turbine, said gears operativelycoordinating the rotors for opposed revolution at substantially coequalspeeds.

2. The combination of claim 1 wherein one of the rotors isantifrictionally journaled by a ball thrust bearing at one end on theinner rotor, and

at its other end by a similar bearing associated with the motivatingmedium inlet manifold.

3. The combination of claim 1 wherein the outer rotor isantifrictionally journaled about an exhaust manifold integral with theinner rotor and at its other end by a similar bearing about themotivating medium inlet manifold, and means whereby said rotors may beaxially adjusted and secured in coactive relation.

4. The combination of claim 1 wherein the planetary gearing comprisesgear rings secured in an annular portion of the outer rotor and to theexterior of an annular exhaust manifold extension of the inner rotor,and the cage-like structure embodies a closure for the exhaust manifoldwith integral outlet connections.

, FRANCIS M. BROOKE.

